JP2003176727A - Repair method for high-temperature component and repaired high-temperature component - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a repair method for a high-temperature component which repaires a defect portion and damage penetrating to the rear face side with high accuracy with high quality, and also to provide the repaired high- temperature component. <P>SOLUTION: This method for repairing the high-temperature component used for an energy engine operated at high temperatures has a process for grinding and shaping the defect portion or the damage penetrating to the rear face side from the front face side of the high-temperature component made of a nickel-based alloy or a cobalt-based alloy to form an open tip having a groove shape wherein the front face side is wider than the rear face side; a process for disposing nickel foil such that the nickel foil covers a face exposed in the open tip; and a process for filling a nickel-based alloy brazing material into the open tip from above the nickel foil, heating and melting the brazing material under a heat treatment condition maintaining the heated state for 2-24 hours at a temperature of 1,080-1,270°C, and heating and melting at least one part of a base material and the nickel foil to integrate the base material and the nickel foil with the nickel-based alloy brazing material. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a high temperature component for repairing a high temperature component of an energy engine such as a gas turbine, a steam turbine, a jet engine, etc., particularly a turbine rotor blade, a stator blade, a combustor, and a split ring. The present invention relates to a repair method for parts and a repaired high temperature part.

[0002]

2. Description of the Related Art Nickel-based superalloys and cobalt-based superalloys are used in various high-temperature components such as rotor blades, stationary blades, combustors, split rings, and nozzles of turbine engines that are exposed to high-temperature environments. These hot parts come into direct contact with hot gases and undergo severe thermal cycling and erosion corrosion resulting in significant damage. For this reason, the parts deteriorate in a relatively short period of time, and the original performance as designed is not output. Therefore, replacement or repair is frequently performed.

Since these nickel-base superalloys and cobalt-base superalloys are expensive materials, components are not replaced unless the damage received is fatal, and only the damaged part is brazed. It is repaired and used again to extend the service life.

[0004]

However, when the damage such as cracks generated in the high temperature component penetrates through the wall thickness and opens at about 0.5 mm or more on the back surface side of the component, the brazing material is melted. Since the liquid leaks from the opening and spills on the back side of the component, it is not possible to carry out a reliable brazing work that can guarantee the strength of the repaired portion. The same problem occurs when repairing a thinned portion due to oxidation, corrosion and erosion of the peripheral wall of the cooling passage for air-cooling the turbine rotor blade. Further, the same problem occurs when repairing not only the damage that occurs during operation but also the penetration defect that occurs during the manufacture of the high temperature component.

The present invention has been made in order to solve the above-mentioned problems, and a method and a method for repairing a high temperature component capable of repairing a damage and a defective portion penetrating to the back side with high precision and high quality. The purpose is to provide high temperature parts.

[0006]

A method for repairing a high temperature component according to the present invention is a method for repairing a high temperature component used in an energy engine operated at a high temperature, which is a nickel base alloy or a cobalt base alloy. Grind and shape the damaged or defective part that penetrates from the front side to the back side of the high temperature component
A step of forming a groove-shaped groove in which the front surface side is wider than the back surface side, a step of arranging a nickel foil so as to cover a surface exposed to the groove, and a step from above the nickel foil into the groove. Nickel-based alloy brazing material is filled and temperature is 1080
The brazing material is heated and melted under the heat treatment condition of holding at ˜1270 ° C. for 2 to 24 hours, and at least a part of the nickel foil and the base material is heated and melted to be integrated with the nickel-base alloy brazing material. And a process.

The repaired high temperature component according to the present invention is a repaired high temperature component used in an energy engine operated at a high temperature, the front surface side to the back surface side of the high temperature component made of a nickel base alloy or a cobalt base alloy. By grinding and shaping a damaged or defective portion penetrating the groove, a groove-shaped groove whose front side is wider than the rear side is formed, and a nickel foil is arranged so as to cover the surface exposed to the groove. From above, fill the groove with nickel-base alloy brazing material and
The brazing material is heated and melted under heat treatment conditions of holding at ˜1270 ° C. for 2 to 24 hours, and at least a part of the nickel foil and the base material is heated and melted to form a melt of the nickel-base alloy brazing material. It is characterized by having an alloyed repair site integrated by being diffused or diluted.

The method for repairing high-temperature parts of the present invention can be preferably used for any of the moving blades, stationary blades, combustors, split rings, etc. of turbine engines. The repaired high-temperature parts include moving blades, stationary blades, A combustor and a split ring are provided respectively.

In this case, the thickness of the nickel foil should be 5-10.
The thickness is preferably 0 μm, and most preferably about 10 μm. If the thickness of the foil is less than 5 μm, the foil is easily broken and cannot be handled normally. On the other hand, when the thickness of the foil exceeds 100 μm, it is difficult for the foil to be deformed along the shape of the groove, and the operator cannot bend the foil with fingers.

The groove width on the back surface side of the groove is preferably 1 to 10 mm. If the groove width on the back surface side is less than 1 mm, it will be difficult to mount the nickel foil so as to cover the exposed groove surface to the back surface side, and the melt of the brazing material will not be sufficiently supplied to the back surface side. Is. On the other hand, if the groove width on the back surface side exceeds 10 mm, when the nickel foil melts and loses its strength, the melt of the brazing material leaks to the back surface side of the groove, resulting in poor melting and poor shape. Because.

When the damaged portion is the peripheral wall of the cooling hole for air-cooling the high temperature component, the peripheral wall of the cooling hole is ground and shaped,
Form a groove-shaped groove whose front side is wider than the back side, arrange a nickel foil so as to cover the exposed surface of the groove, and place a nickel-based alloy brazing material in the groove from above the nickel foil. Fill by pushing in, temperature 1080-1270
After heating and melting the brazing material under heat treatment conditions of holding at 2 ° C for 2 to 24 hours, at least a part of the nickel foil and the base material is melted and integrated with the nickel-base alloy brazing material, Drill a cooling hole of the size and shape before the peripheral wall is damaged. As a result, the cooling holes are restored to the size and shape according to the design specifications, and there is no risk of becoming a starting point for highly dangerous damage such as cracks.
The service life of hot parts is further extended.

Nickel-based alloy brazing materials are Ni, C
Melting point 1080 containing r, Co, W, Ti, Al, B
〜1270 ℃ low melting point alloy powder and Ni, Cr, Co, W
It is preferable that the high melting point alloy powder having a melting point of 1200 ° C. or higher containing ## STR3 ## is mixed at a ratio of 3: 7 to 7: 3. The nickel-based alloy as the base material is, for example, Inconel 738LC (Cr 15.70 to 16.30%, Co 8.00 to 9.00%,
Ti3.20-3.70%, Al3.20-3.70%, W2.40-2.80
%, Mo1.50-2.00%, Ta1.50-2.00%, C0.09-0.
13%, B0.01% or less, P0.01% or less, S0.01% or less), and as an example of the composition of the low-melting Ni-based alloy powder, Ni-8-12Cr-16-20Co-2- 3.5Mo-
1.5-2.5W-5-9Ta-7.5-10Ti-8.5-10.5Al-
1 to 3 Nb-0.5 to 3.5B-0.35Zr, and as an example of the composition of the high melting point Ni-based alloy powder, Ni-16 to 18Cr- to 5Co.
-~ 3.5W- ~ 1.0Ta- ~ 1.0Ti- ~ 1.0Al-0.15 ~
0.3C-0.01-0.03B--0.1Zr can be mentioned, respectively. The mixing ratio of the low melting point Ni alloy powder was 30.
If it is less than wt%, the sintering will not proceed sufficiently. on the other hand,
If the blending ratio of the low melting point Ni alloy powder exceeds 70% by weight, the liquid phase becomes too large and sufficient strength cannot be obtained.

The effects of each component added to Ni are as follows.

First, Cr is an alloy component that imparts oxidation resistance and corrosion resistance to the alloy. Co is a γ'phase (Ni ₃ A
The formation of l) increases the solid solution limit of Al and Ti, which are alloy components effective for improving high temperature strength, at high temperature, and consequently contributes to improvement of high temperature strength.
W has the effect of solid solution strengthening and contributes to the improvement of high temperature strength. Ta contributes to the improvement of high temperature strength by solid solution strengthening and precipitation strengthening by the γ'phase.

Ti and Al contribute to the improvement of high temperature strength by precipitation strengthening by the γ'phase. C forms a carbide,
It mainly strengthens the grain boundaries and contributes to the improvement of high temperature strength. B and Zr increase the bond strength of the grain boundary and improve the high temperature strength.

The effect of addition of each alloy component is the same as that of the Ni alloy powder having a high melting point, that is, N having a high melting point.
Mo, which is not contained in the i alloy powder, has the effect of solid solution strengthening like W, and contributes to the improvement of high temperature strength. Also, N
Similar to Ti, b forms a γ ′ phase together with Al and contributes to the improvement of high temperature strength. Furthermore, Co, Mo, Ta, T
i, Al, and B are added in a larger amount than the Ni alloy powder having a high melting point, and this is for the purpose of lowering the melting point of the alloy powder, and B is particularly effective.

The composition range of the alloying components in each alloy powder is adjusted so that the addition effect of each alloying component is exerted after the melting point is adjusted and after mixing and reacting at a predetermined mixing ratio.
It was decided in consideration that no harmful embrittlement phases would occur.

Before heating, the Ni alloy powder (L) having a low melting point is disposed between the Ni alloy powder (H) having a high melting point, but the Ni alloy powder (L) is melted by heating,
The molten powder fills most of the gaps between the Ni alloy powder (H) by the capillary phenomenon.

The heating is preferably carried out at a temperature of 1080 to 1270 ° C. and a condition of holding for 2 to 24 hours. Here, if the heating temperature is lower than 1080 ° C., the liquid phase due to the capillary phenomenon does not occur, and if the heating temperature exceeds 1270 ° C., the base material is more easily melted. Further, in the present invention, it is preferable to further perform stepwise heat treatment after the above heat treatment (sintering). Specifically, it is heated at 1120 ° C. ± 10 ° C. for 2 to 4 hours (the former), and further at 850 ° C. ± 10 ° C. for 16 to 24.
Heat for an hour (latter).

Here, the former heating is performed by the γ'phase (N) in the base metal precipitated in the cooling process in the heat treatment for sintering.
i ₃ Al intermetallic compound), the temperature is set to 1120 ° C. to prevent solid solution of the γ ′ phase and initial melting, and the treatment time is diffusion of each alloy component. In order to proceed sufficiently, The latter heating is performed in order to uniformly precipitate the γ ′ phase, and is 850 ° C. in order to make the precipitation state of the γ ′ phase uniform and fine, and 16 to 24 in order to precipitate in accordance with the alloy composition. It was time processing.

The area ratio of pores in the Ni-based sintered alloy after heat treatment is preferably ˜5%. This is because generation of pores cannot be avoided by this type of sintering method, but if it exceeds 5%, the strength and ductility of the alloy are adversely affected.

The Ni-based sintered alloy can be used for, for example, bulk forming, coating, and local overlaying. Here, the bulk molding is performed by pressing the powder of the Ni-based sintered alloy into the shape of the wing material and then sintering the powder. The coating is performed by spraying the Ni-based sintered alloy powder on a thinned portion such as high temperature oxidation by a low pressure plasma spraying method or a high speed flame spraying method, and then heating and sintering. The local build-up is one in which the Ni-based sintered alloy powder is built up on a repair target portion such as a cracked portion and then sintered.

[0023]

Various preferred embodiments of the present invention will be described below with reference to the accompanying drawings. In the present embodiment, an example will be described in which various types of high temperature parts used in a gas turbine engine for power generation are repaired by brazing.

As shown in FIG. 1, the gas turbine engine 1 for power generation includes a fuel supply pipe 2, 4, nozzles 3, 5, a combustor inner cylinder 6, a combustor tail cylinder 7, a stationary blade 8 and a moving blade 9. The turbine blade 10, the split ring 11, the compressor (supercharger) 12, the compressed air introduction port 13, and the bypass valve 14 are provided, and the main fuel flows from the plurality of premixing nozzles 3 through the fuel supply pipe 2 into the combustor. The air that is injected into the compressor (supercharger) 12 through the compressed air introduction port 13 is mixed and burned, and the combustion gas rotates the turbine blade 10. There is. At the start of operation, pilot fuel is supplied to the fuel supply pipe 4 and injected from the pilot nozzle 5 for ignition.

The combustor comprises an inner cylinder 6 in which the injection holes of the nozzles 3 and 5 are open, and a tail cylinder 7 following the inner cylinder. The rear end of the combustor transition piece 7 is opened so as to blow the combustion gas to the turbine blade 10. Also, the combustor transition piece 7
A bypass pipe provided with a bypass valve 14 is connected in the middle of. The peripheral wall forming the combustor transition piece 7 is made of a nickel-base heat-resistant alloy.

A stationary blade 8 and a moving blade 9 which form a turbine blade 10.
Are alternately arranged repeatedly. The split ring 11 surrounds the gap between the stationary blade 8 and the moving blade 9 from the outside so that the combustion gas does not leak to the outside through the gap between the stationary blade 8 and the moving blade 9. Is provided. The peripheral wall forming the split ring 11 is made of a cobalt-base heat-resistant alloy.

As shown in FIG. 2, a large number of air cooling through holes 94 are formed in the blade body 91 of the moving blade 9. A large number of similar air cooling through holes (not shown) are also formed in the stationary blade 8.

Example 1 With reference to FIGS. 2 and 3,
As Example 1, a case will be described in which a penetration crack in a gas turbine blade made of a Ni-based alloy (IN738LC) is repaired by brazing.

As shown in FIG. 2, the turbine rotor blade 9 includes a blade main body 91 extending in a circumferential direction, a platform 92 provided at a base portion on the inner peripheral side of the blade main body 91, and an inner peripheral side of the platform 92. It is a precision casting product that is integrated with the fixing portion 93 provided in the. The wing body 91 has a hollow structure,
In order to air-cool the blade body 91, a large number of holes 94 penetrating the blade body from the front surface side to the back surface side are formed in series along the length of the blade body 91.

When the moving blade 9 is used under severe conditions of high temperature and high stress, as shown in FIG. 2, a through crack 99 called a tip thinning crack is easily generated at the tip portion of the blade body 91, and the platform A through crack 99 called a platform crack is likely to occur at the edge of 92. Further, the surface of the peripheral wall of the through hole 94 for air cooling is scraped off due to oxidation, corrosion and erosion, and the diameter of the hole 94 is enlarged on the surface side. In order to safely operate the gas turbine, it is necessary to repair these cracks and thinned parts.

Next, the case of repairing a damaged portion received by the moving blade platform will be described in detail with reference to FIG.

FIG. 3A is an enlarged sectional view showing the platform crack 99 generated at the edge of the platform 92. As shown in the figure, the crack 99 penetrates the thickness of the platform 92 and reaches the back surface side. The portion of the crack 99 is ground with a grindstone or the like to form a groove 100 as shown in FIG. The groove 100 is formed in a groove shape in which the front surface side (outer peripheral surface side) is wider than the rear surface side (inner peripheral surface side), and the rear surface side (inner peripheral surface side) has a groove width of 1 to 10 mm. . The exposed surface 101 of the groove is appropriately inclined so that the groove width on the surface side (outer peripheral surface side) does not become too large.

After degreasing and cleaning the exposed surface 101 of the groove,
As shown in FIG. 3C, the nickel foil 102 is arranged along the groove exposed surface 101, and the nickel foil 102 covers the entire exposed surface 101. The thickness of the nickel foil 102 is 10
It is μm, and has both flexibility that allows an operator to easily bend it with fingers and strength that does not break by normal handling.

A brazing material containing 45% by mass of the low melting point nickel-based alloy powder and 55% by mass of the high melting point nickel-based alloy powder is pressed onto the nickel foil 102, and as shown in FIG. , The brazing part 103 is formed. In this case, the low melting point nickel-base alloy powder has a melting point of 1080 to
Ni-8-12Cr-16-20Co-2-3.5M at 1270 ℃
o-1.5 to 2.5W-5 to 9Ta-7.5 to 10Ti-8.5 to 10.5A
The alloy powder has a composition of 1-1 to 3Nb-0.5 to 3.5B-0.35Zr, and the high melting point nickel-base alloy powder has a melting point of 1200 ° C.
Above Ni-16-18Cr--5Co--3.5W--1.0T
a- ~ 1.0Ti- ~ 1.0Al-0.15 ~ 0.3C-0.01 ~ 0.03
It consists of alloy powder having a composition of B− to 0.1 Zr.

After brazing, the rotor blades 9 were placed in a heat treatment furnace and heat treated under the conditions of 1080 to 1270 ° C. for 2 to 24 hours. As shown in FIG. The brazed part 103 and the nickel foil 102 were sintered and integrated, and integrated with the base material of the platform 92. Subsequently, solution strengthening and aging for strength increase, ie, 1
A two-step heat treatment of 120 ° C. × 2 hours + 850 ° C. × 24 hours was performed.

Further, the extra portion of the brazing portion 103 was ground with a grindstone or the like, and the surface of the repaired portion was made flat as shown in FIG. 3 (f).

According to the first embodiment, since two kinds of Ni-based alloys are mixed and heated to repair the moving blade 9, a capillary phenomenon occurs between the low-melting powder and the high-melting powder, and the strength is increased. It is possible to obtain a sufficient alloying repair portion 103.
In addition, since the stepwise heat treatment is performed after the heating for sintering, the alloying repaired portion 103 in which the γ'phase is uniformly precipitated in the base material and the strength is further increased can be obtained.

(Embodiment 2) Next, referring to FIG. 4, as a second embodiment, a case of repairing a damaged portion due to oxidation, corrosion, and erosion of a peripheral wall of a cooling hole of a gas turbine blade made of a Ni-based alloy (IN738LC) will be described. While explaining.

FIG. 4A is an enlarged sectional view showing a damage 95 caused by oxidation, corrosion, and erosion generated in the cooling hole 94 of the blade body 91. As shown in the figure, the damage 95 is caused by reducing the peripheral wall of the cooling hole 94 so as to expand the hole diameter on the surface side of the blade body 91.

The damaged portion 95 is ground with a grindstone or the like to form a groove 100 as shown in FIG. 4 (b).
The groove 100 is formed in a groove shape in which the front surface side (outer peripheral surface side) is wider than the rear surface side (inner peripheral surface side), and the groove width on the rear surface side (inner peripheral surface side) is 5 mm on average. The exposed surface 101 of the groove is appropriately inclined so that the groove width on the surface side (outer peripheral surface side) does not become too large.

After degreasing and cleaning the exposed surface 101 of the groove,
As shown in FIG. 4C, the nickel foil 102 is arranged along the groove exposed surface 101, and the exposed surface 101 is entirely covered with the nickel foil 102. The thickness of the nickel foil 102 is 10
It is μm, and has both flexibility that allows an operator to easily bend it with fingers and strength that does not break by normal handling.

A brazing material containing 45% by mass of the low melting point nickel-based alloy powder and 55% by mass of the high melting point nickel-based alloy powder is pressed onto the nickel foil 102, and as shown in FIG. , The brazing part 103 is formed. In this case, the low melting point nickel-base alloy powder has a melting point of 1080 to
Ni-8-12Cr-16-20Co-2-3.5M at 1270 ℃
o-1.5 to 2.5W-5 to 9Ta-7.5 to 10Ti-8.5 to 10.5A
The alloy powder has a composition of 1-1 to 3Nb-0.5 to 3.5B-0.35Zr, and the high melting point nickel-base alloy powder has a melting point of 1200 ° C.
Above Ni-16-18Cr--5Co--3.5W--1.0T
a- ~ 1.0Ti- ~ 1.0Al-0.15 ~ 0.3C-0.01 ~ 0.03
It consists of alloy powder having a composition of B− to 0.1 Zr.

After brazing, the rotor blades 9 were placed in a heat treatment furnace and heat treated under the condition of 1,080 to 1,270 ° C. for 2 to 24 hours, and alloying repair was performed as shown in FIG. The brazing part 103 as a part and the nickel foil 102 were sintered and integrated with the base material of the blade body 91. Subsequently, in order to increase the strength, solution treatment and aging, that is, two-step heat treatment of 1120 ° C. × 2 hours + 850 ° C. × 24 hours were performed.

Further, the extra portion of the brazed portion 103 was ground with a grindstone or the like, and the surface of the repaired portion was made flat as shown in FIG. 4 (f). Then, the brazing portion 103 was perforated by using electric discharge machining to form a cooling hole 94 having a predetermined size and shape as shown in FIG. As a result, the cooling holes 94 having the designed size and shape before being damaged were reproduced in the moving blade 9.

According to the second embodiment, since two kinds of Ni-based alloys are mixed and heated to repair the rotor blade 9, a capillary phenomenon occurs between the low melting point powder and the high melting point powder, and the strength is increased. It is possible to obtain a sufficient alloying repair portion 103.
In addition, since the stepwise heat treatment is performed after the heating for sintering, the alloying repaired portion 103 in which the γ'phase is uniformly precipitated in the base material and the strength is further increased can be obtained.

[0046]

As described above in detail, according to the present invention, a penetration damage or a penetration defect having a back side opening amount of 0.5 mm or more is prevented without the melt of the brazing material dripping on the back side of the component. The brazing can be surely repaired, and a high-quality repaired part satisfying the required level of guaranteed strength can be obtained. For this reason, it is possible to repair the damaged parts that were conventionally replaced with new ones and discarded, and to reuse them, so that the maintenance cost can be significantly reduced.

[Brief description of drawings]

FIG. 1 is a cross-sectional view of a main part showing an outline of a gas turbine.

FIG. 2 is a perspective view showing the appearance of a damaged gas turbine rotor blade.

3A to 3F are process diagrams showing a method for repairing a high temperature component according to an embodiment of the present invention.

4A to 4G are process drawings showing a method for repairing a high temperature component according to another embodiment of the present invention.

[Explanation of symbols]

2, 4 ... Fuel supply pipe, 3, 5 ... Nozzle, 6 ... Combustor inner cylinder, 7 ... Combustor transition piece, 8 ... Shizuka, 9 ... moving blades, 10 ... turbine blades, 11 ... split ring, 12 ... Compressor (supercharger), 13 ... Compressed air inlet, 14 ... Bypass valve, 91 ... Wing body, 92 ... Platform, 93: fixed part, 94 ... Through hole (cooling hole), 99 ... Penetration defects (cracks, cracks), 100 ... groove, 101 ... exposed surface of groove 102 ... Ni foil, 103 ... Ni alloy part (alloying repair part).

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁷ Identification code FI theme code (reference) C22F 1/10 C22F 1/10 K F01D 5/28 F01D 5/28 // C22F 1/00 614 C22F 1 / 00 614 651 651B 691 691B 691C (72) Inventor Koji Takahashi 2-1-1, Niihama, Arai-cho, Takasago-shi, Hyogo Mitsubishi Heavy Industries, Ltd. Takasago Plant (72) Masahiko Onda 2-1-1, Niihama, Arai-cho, Takasago, Hyogo Prefecture No. 1 Mitsubishi Heavy Industries, Ltd. Takasago Plant (72) Inventor Yasushi Takeuchi 2-1-1, Niihama, Arai-cho, Takasago City, Hyogo Prefecture Mitsubishi Heavy Industries Ltd. Takasago Plant F-term (reference) 3G002 EA06

Claims (8)

[Claims] 1. A method for repairing a high temperature component used in an energy engine operated at high temperature, the damage or defect penetrating from a front surface side to a back surface side of a high temperature component made of a nickel base alloy or a cobalt base alloy. Grinding and shaping the part to form a groove-shaped groove in which the front surface side is wider than the back surface side, a step of arranging a nickel foil so as to cover the surface exposed to the groove, and the nickel foil From the above, the groove is filled with a nickel-base alloy brazing material, and the temperature is set to 1080 to 1270 ° C for 2 to 2
Heating and melting the brazing material under a heat treatment condition of holding for 4 hours, and at least part of the nickel foil and the base material being heated and melting to be integrated with the nickel-base alloy brazing material. A method for repairing high temperature parts, which is characterized in that 2. The thickness of the nickel foil is 5 to 100 μm.
The method of claim 1, wherein: 3. The groove width on the back surface side of the groove is 1 to 10 mm.
The method of claim 1, wherein: 4. The damaged portion is a peripheral wall of a cooling passage for air-cooling a high temperature component, and the peripheral wall of the cooling passage is ground and shaped to form a groove-shaped groove whose front side is wider than the rear side. A nickel foil is arranged so as to cover the surface exposed to the groove, and a nickel-base alloy brazing material is filled into the groove from above the nickel foil, and the temperature is set to 1080 to 1270 ° C.
The brazing material is heated and melted under a heat treatment condition of holding for 24 hours, and at least a part of the nickel foil and the base material is heated and melted to be integrated with the nickel-base alloy brazing material and then cooled. The method of claim 1, wherein the cooling holes are sized and shaped before the peripheral wall of the passage is damaged. 5. The nickel-base alloy brazing material is N
Melting point 1 containing i, Cr, Co, W, Ti, Al, B
Low melting point alloy powder of 080 to 1270 ° C and Ni, Cr, C
2. The method according to claim 1, wherein the high melting point alloy powder containing o and W and having a melting point of 1200 [deg.] C. or higher is mixed at a ratio of 3: 7 to 7: 3. 6. A repaired high temperature component for use in an energy engine operated at high temperature, wherein a damaged or defective portion penetrating from the front surface side to the back surface side of a high temperature component made of a nickel base alloy or a cobalt base alloy is ground. A groove-shaped groove is formed so that the front surface side is wider than the back surface side, nickel foil is arranged so as to cover the surface exposed to the groove, and a nickel base is placed in the groove from above the nickel foil. The alloy brazing material is filled and the brazing material is heated and melted under a heat treatment condition of holding the temperature at 1080 to 1270 ° C. for 2 to 24 hours, and at least a part of the nickel foil and the base material is heated and melted to A repaired high-temperature component having an alloying repaired part integrated by being diffused or diluted with a melt of a nickel-base alloy brazing material. 7. The nickel-base alloy brazing material is N
Melting point 1 containing i, Cr, Co, W, Ti, Al, B
Low melting point alloy powder of 080 to 1270 ° C and Ni, Cr, C
7. The high temperature component according to claim 6, which is composed of a mixture of a high melting point alloy powder containing o and W and having a melting point of 1200 ° C. or higher at a ratio of 3: 7 to 7: 3. 8. The high temperature component according to claim 6, wherein the alloying repaired portion is a part of any of a rotor blade, a stator blade, a combustor and a split ring of a turbine engine.